For assessing the inlet distortion's effects on the stability and performance of turbofan engine

a two-dimensional method was developed.The unsteady two-dimensional inviscid integral Euler's equations were used;units were divided along the axial and circumferential directions and solved by time-matching.Simulations of a two spool mixed flow turbofan engine show that this method would obtain the distortion transfer curves along the flow path

which can assess the attenuation of components such as fan or high pressure compressor for distortion.Capabilities to resist the total pressure and total temperature distortion were analyzed for typical operating points in the flight envelope

and the most dangerous point was confirmed;under the given total pressure distortion condition

the turbofan engine's thrust decreases and the specific oil consumption increases

and the maximum amounts of change are 10.5% and 11.7% respectively.